Extendable and controllable flight vehicle wing/control surface assembly

Abstract

The apparatus of the invention allows flight vehicle and/or guided munition wings and control surfaces to be secured in a retracted and locked position prior to the launch by a control surface retainer. An electro-mechanical differential control system preferably releases the control surface retainer, extends the control surfaces, and servo controls the control surfaces subsequent to launch. The invention also provides a method for guiding a flight vehicle and/or guided munition by releasing the flight vehicle's and/or guided munition's control surface from a control surface retainer, extending the flight vehicle's and/or guided munition's wing/control surface assembly using a wing/control surface actuation system, and controlling the flight vehicle's and/or guided munition's control surfaces using a wing/control surface actuation system.

What is claimed is:  
     
       1. An apparatus for controlling a wing/control surface assembly of a guided munition, the assembly comprising a wing and a control surface, the apparatus comprising: 
       a control surface retainer that prevents the wing/control surface assembly from extending prior to launch; and  
       that rotatably removes the wing/control surface a wing/control surface actuation system the control surface retainer and servo control surface with respect to the wing, wherein the rotation that releases the wing/control surface assembly is about a substantially central longitudinal axis of the control surface.  
     
     
       2. The apparatus in  claim 1 , further comprising: a plurality of wing/control surface assemblies; and 
       a uniform wing/control surface deployment system that uniformly deploys the plurality of wing/control surface assemblies.  
     
     
       3. The apparatus in  claim 2 , wherein said uniform wing/control surface deployment system comprises a mechanical link between adjacent wing/control surface assemblies. 
     
     
       4. The apparatus, in  claim 3 , wherein said mechanical link comprises arc bevel gears; each of the arc bevel gears is located on each of the adjacent wing/control surface assemblies, wherein the arc bevel gears mesh with respect to one another. 
     
     
       5. The apparatus in  claim 1 , wherein the control surface retainer comprises: 
       a control surface hinge mounted to the wing;  
       a stow notch fixed in a frame of the guided munition to secure the control surface to the frame; and  
       wherein a rotation of the control surface about a rotational axis releases the control surface from the notch.  
     
     
       6. The apparatus in  claim 1 , wherein said wing/control surface actuation system comprises a differential with one input and two outputs wherein a single rotational input selectably controls one of an actuation of the wing/control surface assembly and a servo control of the control surface. 
     
     
       7. The apparatus in  claim 6 , wherein said differential comprises: 
       a first bevel gear to provide a rotational force input; and  
       a second bevel gear meshed to said first bevel gear such that rotation of said first bevel gear causes said second bevel gear to provide a selectable one of a first output and a second output.  
     
     
       8. The apparatus in  claim 7 , wherein said second bevel gear is positioned at a 90 degree angle to said first bevel gear. 
     
     
       9. The apparatus in  claim 7 , wherein said first output causes said control surface to rotate about a rotation axis with respect to the wing. 
     
     
       10. The apparatus of  claim 7 , wherein said second output causes said wing/control surface assembly to extend outward with respect to the guided munition to a predetermined position. 
     
     
       11. The apparatus in  claim 7 , wherein a selected one of said first output and said second output is selected when a non-selected one of said first output and second output is restricted. 
     
     
       12. The apparatus of  claim 7 , wherein said first output is restricted through the use of a guide block that prevents said control surface from rotating after said control surface clears a stow notch. 
     
     
       13. The apparatus of  claim 12 , wherein said guide block comprises a height reference, said height reference corresponding to the deployed position of the wing/control surface assembly. 
     
     
       14. The apparatus in  claim 7 , further comprising a spring loaded pin moveably mounted in the guided munition frame, the wing further comprising a pin hole, and wherein the second output is restricted by engaging the pin in the pin hole. 
     
     
       15. The apparatus in  claim 2 , wherein the control surface retainer comprises: 
       a control surface hinge mounted to the wing;  
       a stow notch fixed in a frame of the guided munition to secure the control surface to the frame; and  
       wherein a rotation of the control surface about a rotational axis releases the control surface from the notch.  
     
     
       16. The apparatus of  claim 2 , wherein said wing/control surface assembly comprises a differential with one input and two outputs wherein a single rotational input selectably controls one of an actuation of the wing/control surface assembly and a servo control of the control surface. 
     
     
       17. The apparatus in  claim 16 , wherein said differential comprises: 
       a first bevel gear to provide a rotational force input; and  
       a second bevel gear meshed to said first bevel gear such that rotation of said first bevel gear causes said second bevel gear to provide a selectable one of a first output and a second output.  
     
     
       18. The apparatus in  claim 17 , wherein said second bevel gear is positioned at a 90 degree angle to said first bevel gear. 
     
     
       19. The apparatus in  claim 17 , wherein said first output causes said control surface to rotate about a rotation axis with respect to the wing. 
     
     
       20. The apparatus of  claim 17 , wherein said second output causes said wing/control surface assembly to extend outward with respect to the guided munition to a predetermined position. 
     
     
       21. The apparatus in  claim 17 , wherein a selected one of said first output and said second output is selected when a non-selected one of said first output and second output is restricted. 
     
     
       22. The apparatus of  claim 17 , wherein said first output is restricted through the use of a guide block that prevents said control surface from rotating after said control surface clears a stow notch. 
     
     
       23. The apparatus of  claim 22 , wherein said guide block comprises a height reference, said height reference corresponding to the deployed position of the wing/control surface assembly. 
     
     
       24. The apparatus in  claim 17 , further comprising a spring loaded pin moveably mounted in the guided munition frame, the wing further comprising a pin hole, and wherein the second output is restricted by engaging the pin in the pin hole. 
     
     
       25. A method for guiding a guided munition, the guided munition having a wing/control surface assembly including a wing and a control surface, said method comprising the steps of: 
       rotatably releasing the control surface from a control surface retainer, wherein the rotation that releases the wing/control surface assembly is about a substantially central longitudinal axis of the control surface;  
       extending the wing/control surface assembly from the guided munition using a wing/control surface actuation system; and  
       controlling the control surface using the wing/control surface actuation system.  
     
     
       26. The method in  claim 25 , wherein the extending wing/control surface assembly comprises extending the wing/control surface assembly to a fixed position. 
     
     
       27. The method in  claim 26 , wherein the releasing, extending, and controlling comprises releasing, extending, and controlling using a differential. 
     
     
       28. The method in  claim 27 , wherein the releasing, extending, and controlling using a differential comprises releasing, extending, and controlling utilizing one input, a first output, and a second output. 
     
     
       29. The method in  claim 28 , wherein the releasing, extending, and controlling comprises releasing, extending, and controlling utilizing a motor. 
     
     
       30. The method in  claim 28 , further comprising using the first output for releasing the wing/control surface assembly and for controlling the guided munition's control surface. 
     
     
       31. The method in  claim 28 , wherein the extending comprises extending using the second output. 
     
     
       32. The method in  claim 25 , wherein the extending of the wing/control surface assembly comprises extending the wing/control surface assembly to a predetermined position and fixing the wing/control surface assembly at the pre-determined position. 
     
     
       33. The method in  claim 25 , further comprising extending a plurality of wing/control surface assemblies uniformly with respect to one another. 
     
     
       34. An apparatus for controlling a wing/control surface assembly of a flight vehicle, the assembly comprising a wing and a control surface, the apparatus comprising: 
       control surface retainer that prevents the wing/control surface assembly from extending prior to launch; and  
       a wing/control surface actuation system that rotatably removes the wing/control surface assembly from the control surface retainer and servo controls the control surface with respect to the wing, wherein the rotation that releases the wing/control surface assembly is about a substantially central longitudinal axis of the control surface.  
     
     
       35. The apparatus in  claim 34 , further comprising: 
       a plurality of wing/control surface assemblies; and  
       a uniform wing/control surface deployment system that uniformly deploys the plurality of wing/control surface assemblies.  
     
     
       36. The apparatus in  claim 35 , wherein said uniform wing/control surface deployment system comprises a mechanical link between adjacent wing/control surface assemblies. 
     
     
       37. The apparatus, in  claim 36 , wherein said mechanical link comprises arc bevel gears; each of the arc bevel gears is located on each of the adjacent wing/control surface assemblies, wherein the arc bevel gears mesh with respect to one another. 
     
     
       38. The apparatus in  claim 34 , wherein the control surface retainer comprises: 
       a control surface hinge mounted to the wing;  
       a stow notch fixed in a frame of the flight vehicle to secure the control surface to the frame; and  
       wherein a rotation of the control surface about a rotational axis releases the control surface from the notch.  
     
     
       39. The apparatus in  claim 34 , wherein said wing/control surface actuation system comprises a differential with one input and two outputs wherein a single rotational input selectably controls one of an actuation of the wing/control surface assembly and a servo control of the control surface. 
     
     
       40. The apparatus in  claim 39 , wherein said differential comprises: 
       a first bevel gear to provide a rotational force input; and  
       a second bevel gear meshed to said first bevel gear such that rotation of said first bevel gear causes said second bevel gear to provide a selectable one of a first output and a second output.  
     
     
       41. The apparatus in  claim 40 , wherein said second bevel gear is positioned at an angle to said first bevel gear. 
     
     
       42. The apparatus in  claim 40 , wherein said first output causes said control surface to rotate about a rotation axis with respect to the wing. 
     
     
       43. The apparatus in  claim 40 , wherein said second output causes said wing/control surface assembly to extend outward with respect to the flight vehicle to a predetermined position. 
     
     
       44. The apparatus in  claim 40 , wherein a selected one of said first output and said second output is selected when a non-selected one of said first output and second output is restricted. 
     
     
       45. The apparatus of  claim 40 , wherein said first output is restricted through the use of a guide block that prevents said control surface from rotating after said control surface clears a stow notch. 
     
     
       46. The apparatus of  claim 45 , wherein said guide block comprises a height reference, said height reference corresponding to the deployed position of the wing/control surface assembly. 
     
     
       47. The apparatus in  claim 40 , further comprising a spring loaded pin moveably mounted in the flight vehicle frame, the wing further comprising a pin hole, and wherein the second output is restricted by engaging the pin in the pin hole. 
     
     
       48. The apparatus in  claim 35 , wherein the control surface retainer comprises: 
       a control surface hinge mounted to the wing;  
       a stow notch fixed in a frame of the flight vehicle to secure the control surface to the frame; and  
       wherein a rotation of the control surface about a rotational axis releases the control surface from the notch.  
     
     
       49. The apparatus in  claim 35 , wherein said wing/control surface actuation system comprises a differential with one input and two outputs wherein a single rotational input selectably controls one of an actuation of the wing/control surface assembly and a servo control of the control surface. 
     
     
       50. The apparatus in  claim 49 , wherein said differential comprises: 
       a first bevel gear to provide a rotational force input; and  
       a second bevel gear meshed to said first bevel gear such that rotation of said first bevel gear causes said second bevel gear to provide a selectable one of a first output and a second output.  
     
     
       51. The apparatus in  claim 50 , wherein said second bevel gear is positioned at an angle to said first bevel gear. 
     
     
       52. The apparatus in  claim 50 , wherein said first output causes said control surface to rotate about a rotation axis with respect to the wing. 
     
     
       53. The apparatus in  claim 50 , wherein said second output causes said wing/control surface assembly to extend outward with respect to the flight vehicle to a predetermined position. 
     
     
       54. The apparatus in  claim 50 , wherein a selected one of said first output and said second output is selected when a non-selected one of said first output and second output is restricted. 
     
     
       55. The apparatus of  claim 50 , wherein said first output is restricted through the use of a guide block that prevents said control surface from rotating after said control surface clears a stow notch. 
     
     
       56. The apparatus of  claim 55 , wherein said guide block comprises a height reference, said height reference corresponding to the deployed position of the wing/control surface assembly. 
     
     
       57. The apparatus in  claim 50 , further comprising a spring loaded pin moveably mounted in the flight vehicle frame, the wing further comprising a pin hole, and wherein the second output is restricted by engaging the pin in the pin hole. 
     
     
       58. A method for guiding a flight vehicle, the flight vehicle having 
       a wing/control surface assembly including a wing and a control surface, said method comprising the steps of:  
       rotatably releasing the control surface from a control surface retainer, wherein the rotation that releases the wing/control surface assembly is about a substantially central longitudinal axis of the control surface;  
       extending the wing/control surface assembly from the flight vehicle using the wing/control surface actuation system; and  
       controlling the control surface using the wing/control surface actuation system.  
     
     
       59. The method in  claim 58 , wherein the extending wing/control surface assembly comprises extending the wing/control surface assembly to a fixed position. 
     
     
       60. The method in  claim 59 , wherein the releasing, extending, and controlling comprises releasing, extending, and controlling using a differential. 
     
     
       61. The method in  claim 60 , wherein the releasing, extending, and controlling using a differential comprises releasing, extending, and controlling utilizing one input, a first output, and a second output. 
     
     
       62. The method in  claim 61 , wherein the releasing, extending, and controlling comprises releasing, extending, and controlling utilizing a motor. 
     
     
       63. The method in  claim 61 , further comprising using the first output for releasing the wing/control surface assembly and for controlling the flight vehicle's control surface. 
     
     
       64. The method in  claim 61 , wherein the extending comprises extending using the second output. 
     
     
       65. The method in  claim 58 , wherein the extending of the wing/control surface assembly comprises extending the wing/control surface assembly to a predetermined position and fixing the wing/control surface assembly at the pre-determined position. 
     
     
       66. The method in  claim 58 , further comprising extending a plurality of wing/control surface assemblies uniformly with respect to one another. 
     
     
       67. An apparatus for controlling a plurality of wing/control surface assemblies of a guided munition, the assembly comprising a wing and a control surface, the apparatus comprising: 
       a control surface retainer that prevents the wing/control surface assembly from extending prior to launch; and  
       a uniform wing/control surface deployment system that uses a mechanical link between adjacent wing/control surface assemblies to uniformly deploys the plurality of wing/control surface assemblies with respect to the guided munition and servo controls the control surface with respect to the wing.